KR101612860B1 - Ignitor assembly method for micro gas turbine - Google Patents

Abstract

The present invention relates to a micro gas turbine igniter fastening structure. The micro gas turbine igniter fastening structure according to the present invention includes: a combustor (110) which has a cylindrical shape with one side closed, and wherein a through hole (111) is formed on the cylindrical side; a housing (120) which is installed on an inner circumference of the through-hole (111), and is formed with an insertion hole (120a) having a variable diameter in an axial direction of the through-hole (111), and fixes an igniter (130) to the combustor (110); and the igniter (130) which is arranged in the insertion hole (120a), and has one end inserted into the combustor (110). According to the present invention, provided is a micro gas turbine capable of preventing deformation of an apparatus due to thermal stress because of less errors occurred by screw combining, since the housing of the igniter is welded to the combustor. Also, the deformation of the apparatus can be prevented even though the thermal stress is applied, by making the insertion hole formed in the housing of the igniter have the variable diameter. Also, it is possible to combine the igniter and the insertion hole easily even though the sizes of the igniter and the insertion are different, and it is possible to prevent deformation of the apparatus even though the thermal stress is applied, since the insertion hole formed in the housing of the igniter have the variable diameter. Also, the structure of the present invention can seal an inner space more precisely since the sealing member is pressurized when a finishing cap is combined, by forming a protruded part combined to a main body of a gas turbine in the housing of the igniter, and installing the sealing member between the protruded part and the main body of the gas turbine.

Description

TECHNICAL FIELD [0001] The present invention relates to an igniter assembly for an igniter,

The present invention relates to a micro gas turbine igniter fastening structure, and more particularly, to a micro gas turbine igniter fastening structure that minimizes deformation even when thermal stress or the like is applied to an ignition part coupled to a combustor, and more precisely seals the leakage of mixed gas of air and fuel And more particularly, to a micro gas turbine igniter fastening structure capable of preventing a gas turbine ignition.

2. Description of the Related Art Generally, a gas turbine engine is a kind of rotary internal combustion engine. The gas turbine engine includes a compressor that receives air from outside and compresses it to a high pressure, a high-pressure air supplied from a compressor, And a turbine rotated by a high-temperature and high-pressure combustion gas discharged from the combustor.

Recently, power generation systems using a fuel cell or a micro gas turbine as a distributed power source have attracted attention, unlike a large-scale large-scale power plant. Particularly, the micro gas turbine has advantages such as low initial investment cost, small size and light weight compared with reciprocating engine having the same output, and simple structure and low maintenance cost.

Ignition equipment is used to operate these ultra-small gas turbines. The igniter is connected to the combustor, and is configured to combust the high-pressure air supplied from the compressor and the fuel supplied from the fuel tank.

1 is a schematic view of a conventional micro gas turbine. Referring to Fig. 1, a conventional micro gas turbine 10 is screwed into a gas turbine body 11 and a combustor (not shown). That is, screw threads are formed by screw thread formed on the gas turbine body 11 and the igniter 12 formed on the combustor (not shown).

정도이다. 이러한 고온에 의하여 열응력이 발생하게 되며, 이는 장치 변형의 원인으로 작용한다. 이때, 10

가 상승하는 경우 100mm 당 1

정도의 장치의 변형이 발생하게 되므로, 상대적으로 장치의 크기가 작은 초소형 가스터빈의 경우에는 큰 문제점으로 작용한다.When the igniter 12 is screwed into a combustor (not shown), a minute error must necessarily occur. In this case, if the thermal stress is applied, the apparatus is deformed. Specifically, the temperature in the combustor (not shown) is about 1000

Respectively. These high temperatures result in thermal stresses, which can cause device deformation. At this time,

1 per 100mm when rising

Which is a relatively small size of the apparatus, is a big problem in the case of an ultra-small gas turbine.

Further, there is a problem that deformation of the apparatus occurs due to the thermal stress as described above even when a minute difference occurs between the through-holes formed in the gas turbine body 11 and the combustor (not shown) and the size of the igniter 12.

Patent Document No. 10-0093586 (1996.01.04)

SUMMARY OF THE INVENTION The present invention has been conceived to solve the above problems, and it is an object of the present invention to provide an igniter housing having a variable diameter which is formed in an igniter housing which is connected to a combustor by welding or the like, Which is capable of preventing deterioration of durability due to heat and the like. The present invention also provides an ultra-small gas turbine capable of preventing leakage of a mixture gas of air and fuel by sealing with a sealing member interposed between an igniter and a gas turbine body when a finishing cap of an igniter is attached have.

According to an embodiment of the present invention, the micro gas turbine igniter fastening structure includes a combustor 110 having a cylindrical shape with both sides closed and a through hole 111 formed on one side of the cylindrical shape; An insertion hole 120a having a variable diameter in the axial direction of the through hole 111 is formed in the inner circumferential surface of the through hole 111 and the igniter 130 is fixed to the combustor 110, A housing 120; And the igniter 130, which is disposed inside the insertion hole 120a and is inserted into the combustor 110 at one end.

The igniter housing 120 is installed on the inner circumferential surface of the through hole 111 to reduce the diameter of the through hole 111 and to protrude in the radial direction of the through hole 111, A first housing 121 in which a depression 125 is formed; A first protrusion 126 protruding in a radial direction of the first housing 121 and contacting an upper end and an inner circumferential surface of the first housing 121 is formed at one end of the first housing 121, A second housing 122 having the insertion hole 120a formed in close contact with the igniter 130 to fix the igniter 130; And a plurality of moving parts 123 inserted into the depressed part 125 and separated from the side surface of the first housing 121 by a predetermined distance and movable in the radial direction of the through hole 111 .

The igniter housing 120 is spaced from the side surface of the second housing 122 by a predetermined distance and is disposed between the plurality of moving parts 123 and has one side fixed to the side surface of the first housing 121 And a fixing member (124) fixed to the base.

According to another embodiment of the present invention, the micro gas turbine igniter fastening structure is characterized in that the combustor 110 is installed inside the body of the micro gas turbine 10 having a predetermined thickness.

The igniter housing 120 is installed through one side of the main body of the micro gas turbine 10.

The micro gas turbine igniter fastening structure is characterized in that a second protrusion 127 protruding outward along the radial direction of the igniter housing 120 is formed.

The micro gas turbine igniter fastening structure includes a sealing member 140 interposed between the second protrusion 127 and the main body of the micro gas turbine 10 and formed of an elastic material.

The micro gas turbine igniter fastening structure includes a finishing cap 150 coupled to a plane of the igniter housing 120 and pressing the sealing member 140.

The micro gas turbine igniter fastening structure is characterized in that the finishing cap 150 and the igniter housing 120 are screwed together.

According to the present invention, an igniter housing is welded to a combustor to thereby provide a miniaturized gas turbine capable of preventing deformation of the device due to thermal stress due to small errors caused by screwing.

Further, by allowing the insertion hole formed in the igniter housing to have a variable diameter, deformation of the device can be prevented even if thermal stress is applied.

Further, by making the insertion hole formed in the igniter housing have a variable diameter, even if the size of the igniter and the insertion hole is different, the coupling can be easily performed, and deformation of the device can be prevented even if thermal stress is applied.

In addition, by forming a protrusion in the igniter housing that engages with the gas turbine body, and by providing a sealing member between the protrusion and the gas turbine body, the sealing member can be pressed to seal the inner space more precisely when engaging the finishing cap.

1 schematically shows a conventional micro gas turbine;
2 is a schematic cross-sectional view of a micro gas turbine according to a first embodiment of the present invention;
Fig. 3 is an exploded view of the micro gas turbine of Fig. 2; Fig.
4 shows the operation of the micro gas turbine of FIG. 2;
5 is a schematic cross-sectional view of a micro gas turbine according to a second embodiment of the present invention.
6 is a view showing a state in which the finishing cap of the ultra-small gas turbine of Fig. 5 is separated; Fig.
7 shows the operation of the micro gas turbine of FIG.

It is to be understood that the words or words used in the present specification and claims are not to be construed in a conventional or dictionary sense and that the inventor can properly define the concept of a term to describe its invention in the best way And should be construed in accordance with the meaning and concept consistent with the technical idea of the present invention. Therefore, the embodiments described in the present specification and the configurations shown in the drawings are merely the most preferred embodiments of the present invention and are not intended to represent all of the technical ideas of the present invention. Therefore, various equivalents It should be understood that water and variations may be present. In the following description, well-known functions or constructions are not described in detail since they would obscure the invention in unnecessary detail. Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

In the various embodiments, components having the same configuration are represented by the same reference symbols in the first embodiment, and in the other embodiments, configurations different from those of the first embodiment will be described. Hereinafter, a micro gas turbine according to a first embodiment of the present invention will be described in detail with reference to the accompanying drawings.

The micro gas turbine according to the first embodiment of the present invention has a variable diameter insertion hole formed in an igniter housing that is coupled to a combustor by welding or the like so that the durability is prevented from being lowered due to deformation of the device even when thermal stress or the like is applied. The present invention relates to an ultra-small gas turbine which can be used as a gas turbine.

FIG. 2 is a schematic cross-sectional view of a micro gas turbine according to a first embodiment of the present invention, and FIG. 3 is an exploded view of the micro gas turbine of FIG. 2 and 3, the micro gas turbine 100 according to the first embodiment of the present invention includes a combustor 110, an igniter housing 120 installed in the through hole 111 of the combustor 110, And an igniter 130 installed in the insertion hole 120a formed in the igniter housing 120.

The combustor 110 is configured to combust high-pressure air compressed in a compressor (not shown) to generate high-temperature, high-pressure gas and supply it to a turbine (not shown). In the combustor 110, an igniter housing 120 is provided and a through hole 111, which is an area where the igniter 130 is inserted, is formed. The through hole 111 is provided to have a diameter larger than the diameter of the igniter 130. The diameter of the through hole 111 is set to be larger than the diameter of the igniter 130 because the first housing 121 is provided on the through hole 111 to reduce the diameter of the through hole 111. [

정도이다. 이러한 고온에 의하여 초소형 가스터빈(100)에 열응력이 가해지며, 이는 장치 변형의 원인으로 작용한다. 이때, 10

가 상승하는 경우 100mm 당 1

정도의 장치의 변형이 발생하게 되므로, 본 실시 예와 같이 상대적으로 장치의 크기가 작은 초소형 가스터빈(100)의 경우에는 큰 문제점으로 작용한다.When the high-pressure air supplied from the compressor in the combustor 110 is burned, the temperature of the combustor 110 is very high. In this embodiment, the temperature of the combustor 110 is about 1000

Respectively. Due to such a high temperature, thermal stress is applied to the micro gas turbine 100, which causes deformation of the apparatus. At this time,

1 per 100mm when rising

So that it is a big problem in the case of the micro gas turbine 100 having a relatively small device size as in the present embodiment.

The igniter housing 120 is installed in the through hole 111 formed in the combustor 110 and has a structure in which the igniter 130 is inserted and fixed. The igniter housing 120 includes a first housing 121, a second housing 122, And a fixing member 124.

The first housing 121 is for fixing the igniter 130 on the combustor 110 and is provided in the through hole 111. The first housing 121 is installed in the through hole 111 of the combustor 110 and welded to the combustor 110. Even if there is a slight error in the screw connection, if the thermal stress due to the high temperature of the combustor 110 is received, the apparatus is deformed. In this embodiment, however, there is almost no influence due to heat load because it is welded. Since the first housing 121 is provided on the through hole 111 so that the diameter of the through hole 111 is reduced but the diameter of the through hole 111 is larger than the diameter of the igniter 130, (130) is inserted easily as described above.

The first housing 121 is formed with a depression 125 which is recessed in the combustor 110 along the radial direction of the through hole 111. The moving part 123 and the fixing member 124 to be described later are inserted into the depressed part 125 and are separated from each other by the thermal stress due to the separation between the side wall of the first housing 121 and the moving part 123 The deformation of the apparatus can be minimized.

The second housing 122 is for fixing the igniter 130 and is installed in the first housing 121. An insertion hole 120a is formed in the second housing 122, and the igniter 130 is fixedly attached to the inner circumferential surface. One end of the second housing 122 is inserted into the first housing 121. A first protrusion 126 protruding in the radial direction of the first housing 121 and contacting the upper end and the inner circumferential surface of the first housing 121 is formed in the second housing. The first projection 126 together with the depression 125 creates a space for inserting the moving part 123 and the fixing member 124 which will be described later.

Meanwhile, the insertion hole 120a formed in the second housing 122 is provided to have a variable diameter. That is, the second housing 122 is provided so as to extend and retract along the radial direction of the insertion hole 120a. The moving part 123 is disposed adjacent to the outer circumferential surface of the second housing 122 and the second housing 122 is spaced apart from the first housing 121 of the moving part 123 inserted into the depressed part 125 So that it can be stretched and shrunk. In this embodiment, the second housing 122 and the moving part 123 are provided with almost no gap, but a clearance may be formed when the apparatus is manufactured. At this time, the gap may be about 0.02 mm.

The moving part 123 is formed in a thin plate shape and is inserted into the depression 125 so that the diameter of the insertion hole 120a of the second housing 122 can be changed. The moving part 123 is installed so as not to be spaced apart from the second housing 122 but spaced apart from the first housing 122 by a predetermined distance.

The moving part 123 moves to the side wall of the first housing 121 when the diameter of the insertion hole 120a is increased due to the second housing 122 extending along the diameter direction of the insertion hole 120a. That is, even if the diameter of the insertion hole 120a is changed by the separation between the moving part 123 and the first housing 121, the device is not affected.

The insertion of the ignition part 130 is facilitated by the movement of the moving part 123 and the change in diameter of the insertion hole 120a. In particular, there is no problem in the apparatus if the diameter of the ignition unit 130 and the diameter of the insertion hole 120a are precisely matched. However, a slight error may occur during the designing of the apparatus and the diameter of the ignition unit 130 When the insertion hole 120a is formed to be finer than the diameter of the insertion hole 120a, the device may be deformed in the process of inserting the ignition part 130. [ In this embodiment, however, even if the diameter of the ignition portion 130 is made larger than the diameter of the insertion hole 120a, the ignition portion 130 can be easily moved by the movement of the moving portion 123 and the expansion and contraction of the second housing 122 Can be inserted.

The influence of thermal stress caused by the high-temperature combustor 110 hardly occurs due to the movement of the moving part 130 and the change in diameter of the insertion hole 120a. When the thermal stress is applied by the high-temperature combustor 110, the moving part 130 is moved to the side wall of the first housing 121 at a predetermined distance, thereby preventing deformation of the device.

The fixing member 124 is interposed between the pair of moving parts 123 to prevent leakage of mixed gas of air and fuel. The fixing member 124 is provided in the form of a thin plate like the moving part 123 and unlike the moving part 123, the fixing member 124 is provided so as to have no gap with the first housing 121, And are spaced apart from each other by a predetermined distance.

The moving part 123 and the first housing 121 may be spaced apart from each other by about 0.02 mm when the apparatus is manufactured. A slight amount of air-fuel mixture gas may leak due to the separation between the side walls. At this time, since the fixing member 124 is provided so as not to be spaced apart from the side wall of the first housing 121, leakage of the mixed gas can be prevented. It is preferable that the distance between the moving part 123 and the first housing 121 and the distance between the fixing member 124 and the second housing 122 are the same.

Hereinafter, the operation of the micro gas turbine according to the first embodiment of the present invention will be described. 4 is a view schematically showing the operation of the micro gas turbine according to the first embodiment of the present invention. First, the first housing 121 is installed on the through hole 111 of the combustor 110. The diameter of the through hole 111 is reduced by the first housing 121. Thereafter, the moving part 123 and the fixing member 124 are installed in the depressed part of the first housing 121. Specifically, the moving parts 123 are provided in a pair, and the fixing member 124 is interposed between the pair of moving parts 123. [

Then, the second housing 122 is inserted into the first housing 121. At this time, the fixing member 124 has almost no gap with the first housing 121 but is spaced apart from the second housing 122. The moving part 123 has almost no gap with the second housing 122, 1 housing 121 as shown in Fig.

Finally, the ignition portion 130 is inserted into the insertion hole 120a of the second housing 122. When the ignition part 130 is made larger than the insertion hole 120a of the second housing 122, when the ignition part 130 is inserted into the insertion hole 111, when the ignition part 130 is inserted into the second housing 122 are pressed in the radial direction of the insertion hole 122a and the moving part 130 moves toward the first housing 121 so that the diameter of the insertion hole 120a is changed and the ignition part 130 is easily inserted do.

Therefore, according to the present embodiment, the insertion hole 120a formed in the igniter housing 120, which is coupled to the combustor by welding or the like, has a variable diameter, so that even if thermal stress or the like is applied, the durability A small-sized gas turbine is provided.

Next, a micro gas turbine according to a second embodiment of the present invention will be described. The present invention differs from the first embodiment in that a second protrusion 127 is formed in the igniter housing 120. The micro gas turbine 100 according to the second embodiment of the present invention is capable of preventing deformation due to thermal stress and the like according to the first embodiment as well as preventing deformation of the interior of the igniter and the gas turbine body when the finishing cap 150 of the igniter is engaged. The present invention relates to an ultra-small gas turbine which can be sealed more precisely by pressurizing the sealing member 140 so as to prevent leakage of mixed gas of air and fuel.

FIG. 5 is a schematic cross-sectional view of a micro gas turbine according to a second embodiment of the present invention, and FIG. 6 is a view showing a state in which a finishing cap of the micro gas turbine of FIG. 5 is separated. 5 and 6, a micro gas turbine according to a second embodiment of the present invention includes a combustor 110, an igniter housing 120 installed in a through hole 111 of the combustor 110, A sealing member 140 interposed between the igniter housing 120 and the gas turbine body 10; an igniter 130; and an igniter housing 130, which is installed in the insertion hole 120a formed in the housing 120, And a finishing cap 150 installed on an upper surface of the main body 120. Here, since the combustor 110 and the igniter 110 are the same as those of the first embodiment, a duplicate description will be omitted.

The igniter housing 120 includes a first housing 121, a second housing 122, a moving part 123, and a second housing 122. The igniter housing 120 includes a through hole 111 formed in the combustor 110, And a fixing member 124. Since the first housing 121, the moving part 123, and the fixing member 124 are the same as those of the first embodiment, the duplicate description will be omitted.

The second housing 122 is for fixing the igniter 130 and is installed in the first housing 121 and the gas turbine main body 10. An insertion hole 120a is formed in the second housing 122, and the igniter 130 is fixedly attached to the inner circumferential surface.

A second protrusion 127 is formed in the second housing 122 along the radial direction of the insertion hole 120a. The second protrusion 127 is formed to prevent leakage of a mixed gas of air and fuel. The second projection 127 is mounted in the mounting area of the micro gas turbine 100 body formed to correspond to the shape of the second housing 122.

The distance between the side surface of the second housing 122 and the gas turbine main body 10 is determined by the distance between the moving part 123 and the side surface of the first housing 122, (121). As a result, the diameter of the insertion hole 120a can be easily changed.

The sealing member 140 is interposed between the lower surface of the second protrusion 127 of the second housing 122 and the body of the micro gas turbine 100. The gas can be leaked to the gap between the lower surface of the second projection 127 and the main body of the micro gas turbine 100 but the gas leakage can be prevented by the sealing member 140.

Meanwhile, the sealing member 140 is made of a material having elasticity. When the second housing 122 is pressed toward the combustor 110 by the finishing cap 150 described later, the sealing member 140 is pressed to seal the inner space more accurately. In this embodiment, the sealing member 140 uses a gasket, but is not limited thereto.

7 is a diagram showing the operation of the micro gas turbine of FIG. Referring to FIG. 7, the finishing cap 150 is configured to close the upper surface of the igniter 130 and the second housing 122. At this time, the finishing cap 150 is provided to be in contact with the upper surface of the second projection 127 of the second housing 122. The finishing cap 150 is screwed and the sealing cap 140 is pressed by the finishing cap 150 pressing the upper surface of the second projection 127 in the process of screwing. As a result, the gap between the lower surface of the projecting portion and the gas turbine main body 10 becomes smaller, and the inner space can be sealed with precision.

Therefore, even if thermal stress or the like is applied to the igniter 130 coupled to the combustor 110, the deformation can be minimized and the leakage of the mixed gas of air and fuel can be prevented more precisely The micro gas turbine 100 is provided.

It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory only and are not restrictive of the invention, as claimed, and will be fully understood by those of ordinary skill in the art. The present invention is not limited thereto. It will be apparent to those skilled in the art that various substitutions, modifications and variations are possible within the scope of the present invention, and it is obvious that those parts easily changeable by those skilled in the art are included in the scope of the present invention .

10 Conventional micro gas turbine
11 Body
12 Ignitors
100 ultra small gas turbines
110 Combustor
120 Ignition housing
120a insertion hole
121 first housing
122 second housing
123 moving part
124 fixing member
125 depression
126 first protrusion
127 Second protrusion
130 Igniter
140 sealing member
150 Finishing Cap

Claims (9)

A combustor 110 having a cylindrical shape with both sides closed and a through hole 111 formed on one side of the cylindrical shape;
An insertion hole 120a having a variable diameter in the axial direction of the through hole 111 is formed in the inner circumferential surface of the through hole 111 and the igniter 130 is fixed to the combustor 110, A housing 120; And
The igniter (130) disposed inside the insertion hole (120a) and having one end inserted into the combustor (110);
Wherein the gas turbine combustor structure comprises:
The igniter housing 120 is installed on the inner circumferential surface of the through hole 111 to reduce the diameter of the through hole 111 and to protrude in the radial direction of the through hole 111, A first housing 121 in which a depression 125 is formed;
A first protrusion 126 protruding in a radial direction of the first housing 121 and contacting an upper end and an inner circumferential surface of the first housing 121 is formed at one end of the first housing 121, A second housing 122 having the insertion hole 120a formed in close contact with the igniter 130 to fix the igniter 130; And
A plurality of moving parts 123 inserted into the depressed part 125 and spaced from the side surface of the first housing 121 by a predetermined distance and movable in the radial direction of the through hole 111;
Wherein the gas turbine igniter assembly structure comprises: delete The method according to claim 1,
The igniter housing 120 is spaced from the side surface of the second housing 122 by a predetermined distance and is disposed between the plurality of moving parts 123 and has one side fixed to the side surface of the first housing 121 Wherein the fastening member (124) comprises a fastening member (124). 4. The method according to any one of claims 1 to 3,
Wherein the combustor (110) is installed inside the body of the micro gas turbine (100) having a predetermined thickness. 5. The method of claim 4,
Wherein the igniter housing (120) is installed through one side of a main body of the micro gas turbine (100). 6. The method of claim 5,
And a second protrusion (127) protruding outward along the radial direction of the igniter housing (120) is formed in the igniter housing (120). The method according to claim 6,
And a sealing member (140) interposed between the second projection (127) and the main body of the micro gas turbine (100) and made of a material having elasticity. 8. The method of claim 7,
And a finishing cap (150) coupled to a plane of the igniter housing (120) and pressing the sealing member (140). 9. The method of claim 8,
Wherein the finishing cap (150) and the igniter housing (120) are threadedly engaged with each other.

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